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  • Lunar and Planetary Science and Exploration  (4)
  • Spacecraft Design, Testing and Performance  (2)
  • Engineering (General)  (1)
  • 2005-2009  (7)
  • 1
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    Nature of the South Pole on Mars Determined by Topographic Forcing of Atmosphere Dynamics (2005)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Introduction: The observed Springtime (Ls approx. 200) surface albedo in the Martian southern polar region is shown in Figure 1. In general, the hemisphere west of Hellas is marked by relatively high values of surface albedo. In contrast, the hemisphere east of Hellas contains extensive regions of very low surface albedo. One of the brightest features within the western hemisphere is the South Pole Residual Cap (SPRC). The dark region, which dominates the eastern hemisphere, is the "Cryptic" region[1]. The nature of the SPRC has been the source of considerable debate since its identification as CO2 ice by the Viking spacecraft. Two fundamental questions still exist regarding the SPRC s formation, location and stability. First, why is the SPRC offset from the geographic pole? There are no local topographic features or surface properties that can account for the offset in the SPRC. Second, does the SPRC represent a large or a small reservoir of CO2? If the former, then it could possibly buffer the surface pressure. If the latter, then the SPRC may not survive every year.
    Keywords: Lunar and Planetary Science and Exploration
    Type: Lunar and Planetary Science XXXVI, Part 3; LPI-Contrib-1234-Pt-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Titan In Situ Exploration Concepts at JPL (2008)
    In:  Other Sources
    Details
    Publication Date: 2018-06-11
    Description: This slide presentation reviews concepts for exploring Titan via balloon vehicles. The presentation includes information about the baseline options, the deployment scenario, and the balloon technology development.
    Keywords: Lunar and Planetary Science and Exploration
    Format: text
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  • 3
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    Ultra Lightweight Ballutes for Return to Earth from the Moon (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Ultra lightweight ballutes offer revolutionary mass and cost benefits along with flexibility in flight system design compared to traditional entry system technologies. Under funding provided by NASA s Exploration Systems Research & Technology program, our team was able to make progress in developing this technology through systems analysis and design, evaluation of materials and construction methods, and development of critical analysis tools. Results show that once this technology is mature, significant launch mass savings, operational simplicity, and mission robustness will be available to help carry out NASA s Vision for Space Exploration.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA Paper 2006-1698 , 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; May 01, 2006 - May 04, 2006; Newport, RI; United States
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  • 4
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    Albedo of the South Pole on Mars Determined by Topographic Forcing of Atmosphere Dynamics (2005)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The nature of the martian south polar cap has remained enigmatic since the first spacecraft observations. In particular, the presence of a perennial carbon dioxide ice cap, the formation of a vast area of black slab ice known as the Cryptic region and the asymmetric springtime retreat of the cap have eluded explanation. Here we present observations and climate modelling that indicate the south pole of Mars is characterized by two distinct regional climates that are the result of dynamical forcing by the largest southern impact basins, Argyre and Hellas. The style of surface frost deposition is controlled by these regional climates. In the cold and stormy conditions that exist poleward of 60 degrees S and extend 180 degrees in longitude west from the Mountains of Mitchel (about 30 degrees W), surface frost accumulation is dominated by precipitation. In the opposite hemisphere, the polar atmosphere is relatively warm and clear and frost accumulation is dominated by direct vapour deposition. It is the differences in these deposition styles that determine the cap albedo.
    Keywords: Lunar and Planetary Science and Exploration
    Type: Letters to Nature; 435; 184-188
    Format: text
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  • 5
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    Design of a Model Execution Framework: Repetitive Object-Oriented Simulation Environment (ROSE) (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The ROSE framework was designed to facilitate complex system analyses. It completely divorces the model execution process from the model itself. By doing so ROSE frees the modeler to develop a library of standard modeling processes such as Design of Experiments, optimizers, parameter studies, and sensitivity studies which can then be applied to any of their available models. The ROSE framework accomplishes this by means of a well defined API and object structure. Both the API and object structure are presented here with enough detail to implement ROSE in any object-oriented language or modeling tool.
    Keywords: Engineering (General)
    Type: NASA/TM-2008-215299 , AIAA Paper-2008-4860 , E-16568 , 44th Joint Propulsion Conference and Exhibit; Jul 21, 2008 - Jul 23, 2008; Hartford, CT; United States
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  • 6
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    Autonomous flight control for a planetary exploration aerobot (2005)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Robotic lighter-than-air vehicles, or aerobots, provide a strategic platform for the exploration of planets and moons with an atmosphere, such as Venus, Mars, Titan and the gas giants.
    Keywords: Lunar and Planetary Science and Exploration
    Type: AIAA Space 2005; Aug 30, 2005 - Sep 01, 2005; Long Beach, CA; United States
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  • 7
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    Aerocapture Systems Analysis for a Neptune Mission (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A Systems Analysis was completed to determine the feasibility, benefit and risk of an aeroshell aerocapture system for Neptune and to identify technology gaps and technology performance goals. The systems analysis includes the following disciplines: science; mission design; aeroshell configuration; interplanetary navigation analyses; atmosphere modeling; computational fluid dynamics for aerodynamic performance and aeroheating environment; stability analyses; guidance development; atmospheric flight simulation; thermal protection system design; mass properties; structures; spacecraft design and packaging; and mass sensitivities. Results show that aerocapture is feasible and performance is adequate for the Neptune mission. Aerocapture can deliver 1.4 times more mass to Neptune orbit than an all-propulsive system for the same launch vehicle and results in a 3-4 year reduction in trip time compared to all-propulsive systems. Enabling technologies for this mission include TPS manufacturing; and aerothermodynamic methods for determining coupled 3-D convection, radiation and ablation aeroheating rates and loads.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA/TM-2006-214300 , L-19236
    Format: application/pdf
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